Multiple unit projectile



Sept. 3, 1957 L JABLANSKY MULTIPLE UNIT PROJECTILE Filed May 13, 1955 ...Kiln

' JNENToR. Louis Tjuhlunaky ATi-oem: YS

nited States Patent ce 2,864,823 Patented Sept. 3, 1957 MULTIPLE UNIT PROJECTILE Louis Jablansky, New York, N. Y. Application May 13, '1955, Serial No. 568,335

9 Claims. (Cl. 102--49) (Granted under Title `3S, U. S. Code (1952), sec. 266) The invention described herein may be manufactured and used by or for the Government for governmental purposes without the payment to me of any royalty thereon.

This invention relates to a multiple unit projectile.

Multiple unit projectiles used in the past have been fired as a single unit land detonated on a target as a single unit. No provision was made for isolating the blast from the leadingunit from the blast of a following unit, therefor the first blast interfered with the proper functioning of the second blast and seriously reduced the potential penetration and destructive effect otherwise inherent in two or more successive impacts on the same target area.

It is therefore an object of the invention to provide a multiple unit projectile whose component units separate while the projectile is in ight, the following unit striking the target at a time-delay interval after the leading unit strikes, whereby the maximum penetration and destructive effect of the successive impacts of the projectiles on the same spot or area of thetarget maybe attained. t

Another object of the invention is to provide a multiple unit projectile whose leading unit is fitted with an explosive charge of predetermined characteristics while its following unit is tted with `an explosive charge of the same or different characteristics whereby a preselected effect on the target is accomplished.

A further object of the invention is to provide the leading unit of a multiple unit projectile with a propellent charge having a proximity-fuze therein initiated on approach to a target whereby the thrust of its propellent gases separates the leading unit from the following unit and provides an additional or increased speed of the leading unit with consequent augmented penetration and/or destructive effect upon the target.

A still further object of the invention is to provide a multiple unit projectile with a separable connection whereby the leading unit is separated from the following `unit under acceleration from its propellent charge.

A still further object of the invention is to provide a multiple unit projectile with a separable connector element whereby a following unit of preselected demolition characteristics is secured to a leading unit.

Other objects and advantages will be apparent from the following detailed description and the accompanying drawings in which:

Figure 1 is a longitudinal sectional View of a multiple unit rocket projectile illustrating the invention,

Figure 2 is a similar view showing a different` type of following unit, and

Figure 3 is a longitudinal sectional View partly in elevation, showing another` type of following unit.

Referring now to the drawings, 5 identifies the leading unit of a multiple unit rocket and 6 identities the following unit thereof. Housed within a casing 7 of the leading unit 5, Figure l, is an explosive charge 8 which is shown in the drawing as a shaped or cavity charge. It is to be understood that other charges, such as a high explosive charge, a plastic explosive charge or a fragmentation charge may be substituted when different types of targets are t-o be attacked. Mounted in the rear end of the casing 7 is a propellent charge 9 which is ignited by a proximity fuze, not shown, enclosed ina housing 11 in an ogival nose cap 12 secured to the forward end of the casing 7. An antenna 13 extends: from the front of the nose cap 12 and receives impulses reflected from the target which are converted to an electrical charge within the fuze, in known manner, and transmits the charge to an igniter 14 by means of a conductor 15 to initiate the propellent in response to approach of the missile to a substantially predetermined range from the target.

Secured to the rear end of the casing 7 is a nozzle structure 16 including an inwardly directed ogival closure 17 which directs the forces of the expanding propellent gases to a series of jets 18 equally spaced in and about the annular space provided between the leading and trailing units of the missile. On impact with a target the explosive charge 8 is detonated by a base type fuze 19.

The following or trailing unit 6 is housed in a casing 20 and carries on its forward end an ogival windshield 21 closely fitting within a recess formed by the ogival closure 17 forming a part of the nozzle 16 of the leading unit 5. Formed in the interior wall of the nozzle 16 and the exterior wall of the casing 20 are mating semi-circular grooves 22 and 23, respectively, in which a spring ring 24 is tted to form a separable connection between the units. An explosive charge 25 is carried near the forward end of the casing 20, and is detonated on impact by a base type fuze 26. A propellent charge 27 is carried in the rear end of the unit 6 and is ignited by a squib 28 adapted to be connected in a firing circuit, not shown, at the launcher. The explosive charge 25 may also vary as dictated by the tactical purpose of the missile, and may be a high explosive charge, a plastic explosive, a fragmentation charge or a fuzed armor piercing projectile. The units 5 and 6 are assembled after a selection 'has been made to include the units having desired demolition effects, and the assembly launched from a conventional rocket launcher or the propellent charge 27 can be omitted and the assembly red from a mortar when desired.

Figure 2 discloses an example of a combination of units, differing from the one shown in Figure l, wherein a leading unit 5 similar to that of Figure l is shown interchangeably connected with a modified form of following unit. The modified following unit 6 is assembled with a casing 20 which carries in its rear end a propellent charge 28 similar to the charge 28 of Figure l.

Secured in the forward end of the casing 26 is an armor piercing projectile 40 having a base fuze 41 and an explosive charge 42. A point protecting cap 43 is secured to the projectile 40 and has a semicircular groove 23 mating with a similar groove 22 in the nozzle 16 to receive a spring ring 24 and provide a separable connection between the units. An ogival windshield 21 is attached to the cap 43 and is shown as closely fitting within the recess formed by the ogival closure 17 on the nozzle 16 of the leading unit 5.

Figure 3 discloses an example of another combination of units, wherein a leading unit 5 similar to that of Figure 1 is connected with a further modified form of following unit 6a. The following unit 6a is assembled with a casing 20a which carries in its rear end a propellent charge 28a similar to the charge 28 of Figure l. Secured to the forward end of the casing 2da in a fragmentation projectile 50 scored as at 51, and having an explosive charge 52 and a base fuze 53. The nose 54 of the projectile 50 is shaped to closely fit within the recess formed 'The projectile' is then launched and when it approaches ythe target the proximity fuze initiates the propelling charge 91in the leading unit and the units are separated :in -response to thrust developed in the leading unit.v The explosive charge 8 in the vrleading unit 5 penetratesA or weakens `the armor plate, depending upon the type tof explosive Vused,'rand is followed shortly thereafter-fby1the following .unit 6 whose explosive charge 2.5V increases Vthe breach, or, as rshown in Figure 3, scatters `fragments inside vor beyond the armor plate. It -Will 'b'e apparent that the invention vherein disclosed .has great utility and vversatility as a destructive agent against'a wide variety of targets.

While Ifhavedisclosed three forms of the `:invention preferred by me, various changes and modifications vwill .occur to those skilled Vin the art after a study of the present disclosure. Hence the disclosure is'to be taken in an illustrative rather than'a limiting sense; and it is my desire and Vintention to reserve all modifications falling Within .the scope'of the subjoinedclaims.

Having now fully disclosed the invention, what I claim Y and desire to` secure by Letters `Patent is: o

l. In a multiple unit projectile, a plurality offseparable units releasably connected in 'axial alignment, a propelling charge and an explosive charge carried by the `leading one of said units, an explosive charge carried by thersecond of said units, means releasably securing Atogether said first and second units, said units being iseparated'in response to thrust developed by initiation of 'the propelling charge of said first unit, and a proximity *fuze in said first unit initiating the propelling :charge therein .on approach to a target. A

2. fIn a multiple lunit rocket projectile, a plurality of coax-ially aligned separable units;l each unit having a propellent ,charge in itsrear end and an explosive charge in itsforward end, la proximity fuze in the yleading unit igniting `its .propellent charge when said fuze is activated by approach to a target, and detachable means normally connecting said units ,in :coaxial alignment and releasing said leading unit for free flight in response to increased 'speed'whe'n its propellent charge is :ignited by said vproximity fuze. Y

3. In a multiple unit rocket projectile, a leading unit and 'a following 'unit in coaxial alignment therewith, -ea'ch unit carrying ya propellent 'charge 'and a 'demolition charge,

interengaging lseparablemeans therebetween whereby said following unit having Aa selecteddemolition characteristic is secured tozsaid .leading unit with its kdemolition charge axially spaced from the 'demolition charge in said leading unit, said leading unit being projected axially forwardly :of said following unit 'on initiation of its propellent charge to produce successive demolition effects ion the same a-rea of the target, anda proximity fuze in 'said leading unit initiating the propelling charge thereinin yresponse to approach to a target. Y

4.1111 .a .multiple unit rocket projectile, a first unit and a second unit in coaxial alignment therewith, yeach unit .having a propellent charge `in 'its rear -en'd and a demolition charge in its forward end, separablemeans normally vconnecting said'first and second unitsin Vcoaxial alignment, and a proximity fuze carried by 'said first vunit AAfor Vigniting the propellent :charge therein when said fuze is activated by approach to a target, said `separable means releasing said first unit under acceleration from its propellent charge to increase the speed of said first unit.

5. In a multiple unit projectile, a plurality of separable units releasably connected in axial alignment, a propelling charge and a shaped explosive .charge carried by the leading one of said units, a propelling charge and a shaped explosive charge carried by the second of said units,V

means releasably securing together said first and second units, said units being separated during ight in response to thrust developed by initiation Vof 4the propelling charge of said first unit, and fuze means carried by said first unit and initiating the propelling charge therein in response to approach-of said projectile to a'target.

V6. In a multiple unit projectile, a plurality ofy separable units releasably connected in axial alignment, a propelling charge and a'shaped explosive charge carried bythe leading lone of said units, a propelling charge and an armor piercing projectile carried bythe second of said units, means freleasably'secuing together said rst and second units, saidunits being separated during :flight inl response to thrust developed by initiation of the propelling charge iof lsaid first unit, and la proximity fuze in said Ifirst'un'it `initiating the propelling charge therein in response to 'approach to a target., j

7. `In a multiple `unit projectilepa plurality of separable units releasably connected in axial alignment, a Vpropel-` ling -charge and ashaped explosive charge carried by the leading one of said units, a propelling charge and' an explosive fragmentation 1projecti-lecarried by the second of pelling nozzles spaced circumferentially Vabout saidfrecess, afsecond Vself-propelled unit having an ogival nose cap, means'fseparably connecting :said first land second unitsiin axially aligned relation and with said'fnose cap fitting saidoogival recess, an explosive charge carried by each said unit, apropelling charge carriedby each said unit, means operable :to initiate the 'propelling charge of said second unit to launchsaid projectile, and a proximity fuzecarried by'said lirst unit and 'operable to initiate the propelling charge .of said first `'unit and separate -saidunrits in ight by and'in response to approach of said projectile toatarget. j

9. In a multiple unit projectile, `a plurality of .separable units `releasably,'connected in axial4 alignment, a propelling charge and an 'explosive charge .carried ,b y .the leading 'one of said units,.an explosive charge carried by the Asecond ofisaid units, means Vreleasably securingsaid first and second units in tandem,said units` being separated in response to thrust developed by initiation ofthe propelling charge of said .leading unit, and-means carried by said leading unit 'to initiate said propelling charge in response to approachof said projectile toa target.

References Cited in the file of `patent v UNITED STATES'PATEENTS I 728,012 'A t Regan May Vl2, `1903 1,102,653 Goddard July `7,` 1914 1,447,198 Wright.... .Man 6, 1923 

